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C. E. P. GOURDOU.

MONOPLANE WITH SUBSIDIARY PLANES.

APPLICATION FILED SEPT-H119!!!- Patented June 3, 191% 6 SHEETSSHEET I.

C. E. P. GOURDOU.

MONOPLANE WITH SUBSIDIARY PLANES.

APPLICATION FILED SEPT-11.1918.

Patented June 3, 1919.-

6 SHEETS-SHEET 2.

C. E. P. GOURDOU.

MONOPLANE WITH SUBSIDIARY PLANES.

APPLICATION FILED SEPT-H.1918.

I 35fi3 Patented June 3, 1919.

6 SHEETSSHEET 3.

WWI/05 a /es mlrdflw C. E. P. GOURDOU.

MONOPLANE WITH SUBSIDIARY PLANES.

APPLICATION FILED SEPT. n. 1918.

1 5 Patented June 3, 1919.

. 6 SHEETS-SHEET 4.

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m/vmm ZZarjzs .2. flwmzaw C. E. P. GOURDOU.

MONOPLANE WITH SUBSIDIARY PLANES.

APPLICATION FILED SEPT-11.1918.

)1 3@5,58% 45 Patented June 3,1919.

6 SHEETSSHEET 5- WWW; [Zarlas 2 awvioa/ Aime/w C. E. P. GOURDOU.

MONOPLANE WITH SUBSIDDARY PLANES.

APPLICATION FILED SEPT-11.1918.

atented 11116 3, 1919.

6 SHEETS-SHEET 6- I'M/vim diam/es [.2 6; 911 060 AUUHNEY To all whom itmay concern:

cnns neon .ri" GG'UBDOU, STwMANDE, FEANGE, AQSIGNQR "EG HIMSELF AND 3'ADQLIPHE LESEUL L i or sr-Men'nn, r l on.

MQHQELE WITH $UB$IDIAEY BLAKE-i3.

iipecifioation of letters Eetent.

Patented am a. rare.

Application filed deptember 11, leis. serial No. 253,626.

Be it known that T, CHARLES EnooARo PIERRE GoURooU, citizen of thepublic of France, and resident of St-lviand, llrance, (post-officeaddress 8 Avenue de la Courelle) have invented a new and useful lilonoplane with Subsidiary Planes, which improvements are fully set forthin the following specification.

The present invention relates to a monoplane with subsidiary planes, thecharacteristic arrangements of which have been devised with a view toreducing to a minimum the resistance to the forward motion of themachine.

The aeroplane is shown by way or" example in the accompanying drawing.

Figure l is a side view of the machine.

Fig. 2 is a front view of the machine.

Figs. 3 and e are detail views on a larger scale.

Fig. 5 is a front elevation, partly in section, of one of the landingwheels.

Figs. 6, 7, 8, 9, id, 11 and 12 relate to the assembling of the varioustubes constituting the framework or" the aeroplane.

Fig. 13 indicates the point of sup-port oi the control of the warping oithe wing.

Fig. let relates to the control enabling the subsidiary planes to beacted upon in such a way that they incline either both in the samedirection or in opposite directions to one another at the pilots option.

Figs. 15 and 16 relate to the carriage or support of the landing wheels.

Fig. .l-7 shows, in detail one of the balland-socket joints employed.

Fig. 18 is a front view or the iris diaphr'agm that conceals theradiator.

The frame of the main plane 0: comp-rises essentially two longitudinalbearers Z7 embedded on the fuselage and supported at a single part onboth sides of the fuselage by tapered tubular stays c.

Each sta' e consists essentially of a metal- Into the internal screwthread is screwed a tube which widens out at 9' so as to form a for;with two prongs g, between which is embraced the wing arm. orlongitudinal bearer I). Each arm or" the fork is provided with two lugs,one of which, it is fixed to the longitudinal bearer by means of .a bolth, whlle the other which is virtually integral with the end part of theprong and is bent over and down on the other side of the longitudinalbearer b. in Fig. 4 the lug h" of the prong g" is seen, located behlndthe longitudinal bearer. This lug it, like the the ' reason or" themethod of fixing hereinbefore described, and the bending over and downof the second lug of each fork to the opposite side of the longitudinalbearer, the shearing of the bolts it and it under the tensile stressesexerted by the stays is obviated.

The adjustment of the stay is obtained by screwing the tube ,1 more orless into the tube 7. When adjustment is obtained a sleeve is screwedup, covering the extremities of the tubes 9 and 7, the sleeve beingfurthermore secured to the tube 9 by means of a pin. Unscrewing is thusrendered impossible, especially as the pitch of the screw thread on g,which screws on to the upper end of the tube 7, is different from thatof the outer sleeve it should be observed that in this mounting devicewelding is entirely obviated. The stays are reinforced by two stretchedcords 7), d.

The ratio between the total length of the wing and the part of the wingcomprised between the two stays may vary, but will preferably be in theneighborhood of /2 With a view to obviating eddies of air around thelanding wheels, each wheel may be constructed, as indicated in Fig. '5,of a rim a, supported, by means of spokes b by the axle c.

@n the rim a an inner tube (5 is placed, kept in position in the usualway by means of rubbered canvas covers without treads, and over thewhole is placed an outer cover or envelop e of canvas, leather or othersuitable material, completely surrounding the wheel and laced at f,after being placed in position, from the outside, the object of thelacin being to secure the position of the enve 0 around the wheel. T etread consists of an india rubber band which is virtually integral withthe envelop e and which, when this envelop is placed in position lodgesagainst the inner tube d' In order to dismount the wheel all that isnecessary is to undo the lacing at f and remove the outercover whichenables access to be obtained to the inner tube.

As indicated in Fig. 6, if occasion arises to unite two tubes a", I) endto end, they are inserted one in the other for a certain length :0. Thatbeing done, by inserting through one end of one of the tubes a circularmandrel and forcing back the metal around the said mandrel, annularridges c are produced (Fig. 7) which may project equally, or which mayproject unequally, decreasing from one extremity to the other. In thisway an assemblage is obtained which is very strong and which can beexecuted very quickly, dispensing with all screw threads and otherdevices hitherto utilized. The annular ridges instead of being producedoutwardly, may likewise be produced inwardly.

For the purpose of uniting two tubes that cross one another, thefollowing procedure is adopted:-

A box is prepared in two parts d, 6" (Fig. 8) in which, when the twoparts are united to one another, passages f, g are formed, cutting oneanother at the angle at which the tubes to be united are to cross oneanother. On one of the tubes a and at the point where the other tube,1)", is to cross, an elliptical opening is is produced by cutting awaythe metal. The tube a" is then placed in the passage 7 of the box d", e,and this tube is pressed until the hole is comes opposite to the passage9 When this has been effected, the punch shown in Fig. 11, that is tosay, a punch which is conical in the part c" and cylindrical in the partj, is inserted in the hole 9 WVhen the punch has traversed the tube a"until the cylindrical part 7" has enlarged the hole is it is withdrawnand it is found that on the tube a two seatings or bearing surfaces is(Fig. 12) have been formed, comprising external projections lodged insuitably formed cavities in the box (1", e". Through the opening 9"" isthen inserted the tube b", which passes through the tube a from one sideto the other. The two parts d, e of thebox are separated, and theassemblage of the two tubes at", b is consolidated by inserting a pin atthe point of crossing.

The crossing, instead of being at right angles, as indicated by theformation of the bearing surfaces k in Fig. 12, may be made at any angle(Fig. 10).

As indiacted by Fig. 13, which shows a diagrammatic plan of one of thewings a of the aeroplane, the control of the warping takes its point ofsupport at j, on the side of the keelson on the back longitudinal bearerb of the wing, the movement of the wing taking place in the direction ofthe arrow 1.

Fig. 14 shows the control which makes it possible to act on thesubsidiary planes in such a way as to incline them both in the samedirection or in opposite directions to one another at the pilots option.The control lever or stick is movable in all directions about the lowerpoint Z. At Z are arranged two inverted-T axes. m and n are twoconnecting rods with ball-and-socket joints, comprising between them abell-crank lever 0 capable of oscillating about 0. p is the crank of thesubsidiary plane 77. g, g, 9 g are ball-and-socket joints. When thecontrol lever or stick is inclined in the direction of the arrow 1 theplane rises in the direction of the arrow 2. In this movement of thecontrol lever the other plane sinks at the same time in the direction ofthe arrow 4. In this way, by suitable inclina tions of the control leverthe subsidiary planes may be moved in opposite directions.

The movements of the subsidiary planes in the same direction areobtained in the following manner: The ball-and-socket joints 9 arecarried by a rin T, which can slide along the tube Z, Z 0 the broomhandle. The travel of thisring may be effected by any means, and, aswill be realized, the displacement of the ring 1' along the controllever will produce the simultaneous inclination or elevation of the twosubsidiary wings, according as the ring rises or descends along thebroom handle. For the purpose of displacing the ring the followingdevice may be indicated by way of example; the ring is connected bymeans of a link r to a grip lever 1'. When the pilot presses the handlein the direction of the arrow 3 the subsidiary wing descends in thedirection of the arrow 4, which augments the lifting power of the wingas the resistance of the air increases. The lever 1 may be locked ifnecessary.

Figs. 15 and 16 relate to a landing carriage. Each wheel describes anarc of a circle having its center located on the axis t. The back tuberotates about its axis 25'. The front tube t" slides in theball-and-socket guide 10 having for its fixed center the center a.

Fig. 17 shows, with details, one of the spherical bearings employed, theone for example that is utilized on one of the front tubes of the frame.The front tube t" passes through a guide 6 which is welded to aspherical steel socket 7. On to the slide 6 is screwed a secondspherical socket 8. After that conceals the radiator.

mosses being screwed up this cup is provided with a secu in device madeof piano wire. The ball strictly so called, 10, is retained in positionbetween the two spherical sockets and is formed of two welded or pressedflanged plates.

Fig. 18 is a front view of the diaphragm It consists essentially ofblades 11, made of sheet steel, riveted to the pinions 12. These pinions12, which can rotate about axes 13 fixed to the radiator, gear with atoothed rim 1% to which can 'be given a rotary movement about its ownaxis by any suitable means. By rotatingthe rim ii, the rotation of thepinions ,12 about their own axes is produced, and thereby the blades 11are opened or closed according to the of the rim 14a Among the numerousdevices that may be utilized for the purpose of producing rotation ofthe rim 14, the accompanying drawing (Fig. 18) shows two. One of themconsists of a lever 15 virtually integral with one of the pinions 12,upon which force may be exerted by means of a cable 16 The otherconsists of a fork 1? which is fixed to the rim at 18 and 19 and uponwhich force may be exerted by means of a cable 2.0.

Claims:

1. A monoplane with subsidiary wing,

comprising tubular stays starting at both ends from the fuselage for thepurpose of sustaining the Wing at such a bending moments on thelong1tudinal bearers may be equal on all the supports; a device foradjusting the stays uniting the wing to the fuselage; a landing carriagewith its axle supported by four rotatable sliding tubes; wheels with anouter cover completely surrounding each of them and a means forlongitudinal bearer of direction of rotation point that the.

fixing the outer covers; a framework with tubes united end to end bymeans of annular ridges;v and tubes passing through one another withseating surfaces on one of them;

spherical-seated bearingxs on the tubes of the chassis; a diaphragm sutter concealing the radiator; a simultaneous and individual control ofthe subsidiary planes; and the supporting of the warping control on theback the wing.

2. A monoplane with subsidiary wing comprising tubular stays withcentral metal tube and a wooden sheath; stays in two parts screwed intoone another for adjustment and a sleeve with stop pin on the parts thatscrew together; a landing carriage with its axle supported by fourrotary sliding tubes; wheels on the landing carriage with an outer covercompletely surrounding each of them, a lacing device for the purpose ofsecuring the edges of the outer cover, a framework with tubes connectedend to end by means of annular ridges; and tubes crossing one anotherwith seating or bearing surfaces on one of them; balLand-socket jointsformed of two flanges welded plates, held between two spherical cups orsockets; a diaphragm with movable blades in front of the radiator; acontrol lever or stick movable into all positions; connections with thesubsidiary wings by means of crank shafts and a ring sliding along thecontrol; and a support for the warping control on the back longitudinalbearer of the wing.

the presence of siii 1 In testimony whereof I have signed this

